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US-12617550-B2 - Guidance system

US12617550B2US 12617550 B2US12617550 B2US 12617550B2US-12617550-B2

Abstract

The present invention relates to a body ( 2 ) that is an aircraft, at least one engine ( 3 ) that is located on the body ( 2 ) and generates the power required for the flight of the aircraft, and at least one exhaust ( 4 ) that is located on the engine ( 3 ) and transmits the fluid (A) heated inside the engine ( 3 ) due to the operation of the engine ( 3 ) to the outside of the aircraft.

Inventors

  • Fatih Turk

Assignees

  • TUSAS—TURK HAVACILIK VE UZAY SANAYII ANONIM SIRKETI

Dates

Publication Date
20260505
Application Date
20241031
Priority Date
20231221

Claims (10)

  1. 1 . A guidance system ( 1 ) comprising: a body ( 2 ) that is an aircraft, at least one engine ( 3 ) that is located on the body ( 2 ) that generates power required for flight of the aircraft, and at least one exhaust ( 4 ) that is located on the engine ( 3 ) that transmits fluid (A) heated inside the engine ( 3 ) due to operation of the engine ( 3 ) to an outside of the aircraft, wherein at least a guide ( 5 ) that is located on the body and/or on the exhaust ( 4 ), wherein in a way that the guide faces towards the exhaust ( 4 ) outlet, meets air flow (H) formed during the flight of the aircraft and takes in the air flow (H), directs the air flow (H) to an exhaust outlet and thus ensures that the fluid heated and coming out of the exhaust ( 4 ) is dispersed irregularly and/or an exhaust direction is changed, wherein at least one fan ( 501 ) is located inside the guide ( 5 ) that takes the air flow (H) into the guide ( 5 ) by rotating and transmitting the air flow to the exhaust outlet, and wherein at least one opening ( 6 ) that is located on the guide that allows the air flow (H) to enter the guide and thus allows air to be absorbed from an external environment.
  2. 2 . The guidance system ( 1 ) according to claim 1 , characterised by at least one cover ( 7 ) that is movable on the guide ( 5 ) and is triggered by a pilot or autonomously, allowing a flow rate of the air coming out of the guide ( 5 ) to be adjusted.
  3. 3 . The guidance system ( 1 ) according to claim 2 , characterised by at least one control unit ( 8 ) that enables movements of the at least one cover ( 7 ) to be controlled and commands to be transmitted to the guide ( 5 ) for the air flow (H) formed during the flight of the aircraft.
  4. 4 . The guidance system ( 1 ) according to claim 2 , characterised by the at least one cover ( 7 ) that has an open position (I) that allows the air flow (H) coming from the guide ( 5 ) to exit, and a second closed position (II) in which the air flow (H) created by the guide ( 5 ) is almost completely reduced.
  5. 5 . The guidance system ( 1 ) according to claim 2 , characterised by a control unit ( 8 ) that adjusts the guides ( 5 ) positioned on the body ( 2 ) and/or on the exhaust ( 4 ) to provide different flow rates and/or moves the covers ( 7 ) to be in an open position (I) and/or closed position (II) and thus ensures distribution of hot air coming out of the exhaust ( 4 ).
  6. 6 . The guidance system ( 1 ) according to claim 1 , characterised by the guide ( 5 ) that allows the air flow (H), which is almost colder than the fluid coming out of the exhaust ( 4 ) during the flight of the aircraft, to be absorbed and transmitted to the exhaust ( 4 ) outlet.
  7. 7 . The guidance system ( 1 ) according to claim 6 , characterised by a cover ( 7 ) that is removable and compatible with a section form of the guide ( 5 ) and is located in a way that creates a square cross-sectional area inside the guide ( 5 ).
  8. 8 . The guidance system ( 1 ) according to claim 1 , characterised by the guide ( 5 ) that is located on the body ( 2 ) and/or on the exhaust ( 4 ) and creates a different air flow (H) and creates a vortex effect on the fluid (A) discharged from the exhaust ( 4 ).
  9. 9 . The guidance system ( 1 ) according to claim 1 , characterised by the guide ( 5 ) that is located on the exhaust ( 4 ) and ensures that the heated fluid (A) inside the engine ( 3 ) exits the aircraft through multiple exhaust ( 4 ) outlets.
  10. 10 . The guidance system ( 1 ) according to claim 1 , wherein the guide ( 5 ) meets the air flow (H) generated during the flight of the aircraft and provides uneven distribution and/or directional change of the heated fluid (A) coming out of the exhaust ( 4 ) by taking the generated air flow (H) into the guide and transmitting it towards the exhaust ( 4 ) is dispersed irregularly and/or a heated fluid direction is changed.

Description

RELATED APPLICATIONS This application is a Paris Convention, which claims the benefit of priority of Turkish Patent Application No. 2023/017906 filed on Dec. 21, 2023. The contents of the above application is all incorporated by reference as if fully set forth herein in its entirety. FIELD AND BACKGROUND OF THE INVENTION The present invention relates to a guidance system that reduces the thermal signature of the heated fluid discharged from the aircraft. In wartime, various types of missiles are used to hit aircraft and infrared (IR) cameras are used to detect aircraft. Heat-seeking missiles are one of these missile types. There are various versions of heat-seeking missiles. While some follow the exhaust heat, others act according to the distribution of heat coming out of the exhaust by knowing the IR signature of the aircraft, so they can follow more precisely using software algorithms. It is more difficult to obfuscate the missiles that can follow IR. In addition, IR cameras can also detect the type of helicopter according to the IR signature. The heated fluid coming out of the exhaust has the same characteristic heat distribution. Therefore, the aircraft is detected by following the IR signature. In the patent document numbered FR2508098 in the state of the art, a system that allows external air to be drawn under the wheel or track housing of a drive unit to protect a vehicle from infrared detection and directs the drawn air towards the radiator and engine for cooling and combustion is disclosed. In the subject of the invention mentioned in the relevant document, a portion of the air in the system is accelerated by a fan and the flow cross-section is reduced by a circular nozzle. In the utility model document numbered CN217440154U in the state of the art, an anti-infrared hidden shelter system that comprises a shelter body, a generator set, and a heat distribution air outlet is disclosed. In the subject of the invention mentioned in the relevant document, the air outlet in the system is positioned in the shelter body. An electronic temperature fan is attached to the heat distribution air outlet and the electronic constant temperature fan is connected to the generator set. In the United States patent document numbered US20080264034A1 in the state of the art, a system and method for cooling at least a portion of an engine is disclosed. The engine is cooled using a fuel such as a high heat absorbing fuel used for combustion in the engine later. The fuel is used to cool the gases and/or components in the engine, thus cooling the engine, including the exhaust nozzle. SUMMARY OF THE INVENTION By means of a guidance system developed with the present invention, the thermal signature of the aircraft is reduced and the heat-tracking missiles and/or infrared (IR) cameras are deceived and prevented from detecting the aircraft. Another aim of this invention is to ensure that the heated fluid discharged from the aircraft is distributed in different directions and/or irregularly. A guidance system, which is realised to achieve the aim of the invention and defined in the first claim and the claims dependent on this claim, comprises a body that is located on a fixed wing or rotary wing aircraft, which is an airplane, unmanned aerial vehicle or helicopter. The body comprises at least one engine on the body that provides the necessary thrust for aircraft flight. It comprises at least one exhaust that is located on the engine in a way that it will be connected to the engine and allows the heated fluid (A) formed due to the operation of the engine and that needs to be released to the outside to be discharged. A guidance system, which is the subject of the invention, comprises at least one guide that is located on the fuselage and/or on the exhaust in a way that intervenes in the heated fluid (A) coming out of the exhaust and faces the exhaust outlet, opposing the air formed and flowing around the aircraft during the flight of the aircraft, extending outward from the fuselage and taking in the formed air flow, directing the taken air flow (H) to the exhaust outlet and thus ensuring that the fluid (A) coming out of the exhaust by heating is distributed irregularly and/or its direction is changed. The guide can be placed on all systems that transmit the heated fluid (A) on the aircraft to the outside of the aircraft and can cool and/or guide the exiting fluid (A). In one embodiment of the invention, a guidance system comprises at least one fan that acts as a propeller that allows the outside air flow (H) to be taken into the guide and rotates and transmits the received air flow (H) towards the exhaust outlet in the guide. In one embodiment of the invention, a guidance system comprises at least one opening that is located on the guide so that it will be opposite to the air flow (H) and allows the air flow (H) formed around the aircraft to enter the guide. In one embodiment of the invention, a guidance system comprises at least o